CN112725693A - Alloy powder for laser repair of large fan main shaft and laser repair method - Google Patents
Alloy powder for laser repair of large fan main shaft and laser repair method Download PDFInfo
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- CN112725693A CN112725693A CN202011504724.1A CN202011504724A CN112725693A CN 112725693 A CN112725693 A CN 112725693A CN 202011504724 A CN202011504724 A CN 202011504724A CN 112725693 A CN112725693 A CN 112725693A
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- C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
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- C22C38/00—Ferrous alloys, e.g. steel alloys
- C22C38/18—Ferrous alloys, e.g. steel alloys containing chromium
- C22C38/40—Ferrous alloys, e.g. steel alloys containing chromium with nickel
- C22C38/44—Ferrous alloys, e.g. steel alloys containing chromium with nickel with molybdenum or tungsten
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- C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
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- C22C38/00—Ferrous alloys, e.g. steel alloys
- C22C38/02—Ferrous alloys, e.g. steel alloys containing silicon
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- C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
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- C22C38/04—Ferrous alloys, e.g. steel alloys containing manganese
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- C22C38/00—Ferrous alloys, e.g. steel alloys
- C22C38/18—Ferrous alloys, e.g. steel alloys containing chromium
- C22C38/40—Ferrous alloys, e.g. steel alloys containing chromium with nickel
- C22C38/46—Ferrous alloys, e.g. steel alloys containing chromium with nickel with vanadium
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- C—CHEMISTRY; METALLURGY
- C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
- C22C—ALLOYS
- C22C38/00—Ferrous alloys, e.g. steel alloys
- C22C38/18—Ferrous alloys, e.g. steel alloys containing chromium
- C22C38/40—Ferrous alloys, e.g. steel alloys containing chromium with nickel
- C22C38/48—Ferrous alloys, e.g. steel alloys containing chromium with nickel with niobium or tantalum
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- C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
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- C22C38/00—Ferrous alloys, e.g. steel alloys
- C22C38/18—Ferrous alloys, e.g. steel alloys containing chromium
- C22C38/40—Ferrous alloys, e.g. steel alloys containing chromium with nickel
- C22C38/54—Ferrous alloys, e.g. steel alloys containing chromium with nickel with boron
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- C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
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- C23C24/00—Coating starting from inorganic powder
- C23C24/08—Coating starting from inorganic powder by application of heat or pressure and heat
- C23C24/10—Coating starting from inorganic powder by application of heat or pressure and heat with intermediate formation of a liquid phase in the layer
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Abstract
The invention relates to a laser repair method and alloy powder for repair, in particular to a laser repair method and alloy powder for repair of a large fan spindle. The invention aims to solve the technical problems that a cladding layer is easy to peel off and generate tempering color easily in a high-speed service environment when a fan main shaft is repaired by adopting a laser repairing method, the hardness is improved by adopting high carbon and high boron, the cladding thickness is easy to crack, and the hardness is reduced due to tempering treatment of a workpiece by a cladding user, and provides a laser repairing method for a large fan main shaft and alloy powder for repairing. The alloy powder is used as a coating component and is close to a base material without color difference, the thermal deformation is small, the structure is compact, the binding force between the coating and the base material is firm, the coating is thick and does not crack, so that the cladding layer in service does not have the risk of stripping, the hardness after tempering meets the industrial standard, the alloy powder is close to the base material to be repaired and has good weldability, and the alloy powder is very suitable for repairing hundreds of thousands of fan main shafts.
Description
Technical Field
The invention relates to a laser repair method and alloy powder for repair, in particular to alloy powder for laser repair of a large fan main shaft and a laser repair method.
Background
The main shaft of the rotor of the large fan such as an axial flow compressor, a turbine expander and the like produced by using 25Cr2Ni4MoV steel is widely applied to the fields of natural gas, petrochemical industry, power stations, metallurgy and the like, and mainly plays a role in conveying clean air, clean coal gas, inert gas and other gases. The major fan main shaft with the rotating speed of thousands of revolutions and the weight of hundreds of thousands of tons or even dozens of thousands of tons often causes the serious abrasion between the main shaft and the bearing bush due to the overlong service period, the pulling damage of foreign matters and the failure of an oil supply system, thus leading to the failure or even the scrapping of the main shaft of the fan. Some large-scale fan main shafts are repaired by installing shaft sleeves on the main shafts and adopting a thermal spraying or plasma beam cladding mode after being seriously abraded, but the three repairing technologies are gradually eliminated due to the reasons that the processing period of the installed shaft sleeves is long, a thermal spraying coating and a base material are physically combined, the bearing and the wear resistance are insufficient, the service life is short, the thermal output of plasma beam cladding is large, the stress deformation in the cladding process is difficult to control and the like, and the laser repairing method is mostly adopted to repair the fan main shafts at present, but the following problems exist when the laser repairing is adopted:
1. the method is characterized in that stainless steel powder circulating on the market is adopted for repairing, so that a cladding layer is easy to peel off in a high-speed service environment of a fan main shaft due to huge difference between components of the stainless steel and components of a base material, and a tempering color is easy to generate when the stainless steel coating is in service in an environment with the highest temperature of 300 ℃, so that unnecessary risks are brought to customers;
2. after the main shaft of the fan is repaired, the cladding thickness is generally required to be 5.0-6.0 mm, the hardness is 230-290 HB, if stainless steel alloy powder is used to reach the hardness range, elements which are easy to crack during welding, such as high carbon, high boron and the like, are generally required to improve the hardness, and the risk of thick melting and cracking is easily caused;
3. after cladding, a user needs to machine and temper the workpiece, and under the condition of a certain heat treatment system, due to the influence of work hardening, the hardness is improved after machining, and the hardness is reduced after tempering, so that the condition that the workpiece is not in accordance with the acceptance condition is caused.
Disclosure of Invention
The invention aims to solve the technical problems that a cladding layer is easy to peel off and generate tempering color easily in a high-speed service environment when a fan main shaft is repaired by adopting a laser repairing method, the hardness is improved by adopting high carbon and high boron, the cladding thickness is easy to crack, and the hardness is reduced due to tempering treatment of a workpiece by a cladding user, and provides alloy powder for laser repairing of a large fan main shaft and a laser repairing method.
In order to solve the technical problems, the technical solution provided by the invention is as follows:
the invention provides alloy powder for laser repair of a large fan spindle, which is characterized by comprising the following components in parts by weight:
C：0.15～0.18wt％；
Cr：1.0～2.0wt％；
Ni：3.0～4.0wt％；
Mo：0.2～0.5wt％；
Mn：0.0～0.5wt％；
Nb：0.05～0.08wt％；
V：0.08～0.12wt％；
B：0.4～0.7wt％；
Si：0.3～0.6wt％；
the balance being Fe.
Furthermore, the powder of each component is prepared by adopting a vacuumizing nitrogen atomization powder preparation method after being mixed in advance.
Furthermore, the particle size of the prepared powder is 75-120 microns.
Further, C: 0.16-0.17 wt%;
Cr：1.3～1.5wt％；
Ni：3.1～3.5wt％；
Mo：0.25～0.35wt％；
Mn：0.2～0.25wt％；
Nb：0.05～0.065wt％；
V：0.08～0.10wt％；
B：0.45～0.55wt％；
Si：0.35～0.45wt％；
the balance being Fe.
Further, C: 0.17 wt%;
Cr：1.5wt％；
Ni：3.5wt％；
Mo：0.35wt％；
Mn：0.25wt％；
Nb：0.065wt％；
V：0.10wt％；
B：0.55wt％；
Si：0.45wt％；
the balance being Fe.
Further, C: 0.16 wt%;
Cr：1.3wt％；
Ni：3.1wt％；
Mo：0.25wt％；
Mn：0.2wt％；
Nb：0.05wt％；
V：0.08wt％；
B：0.45wt％；
Si：0.35wt％；
the balance being Fe.
The invention also provides a laser repair method for the large fan spindle, which is characterized in that the laser repair method based on the alloy powder for the large fan spindle comprises the following steps:
1) removing a fatigue layer of the large fan main shaft by turning, and pouring 30 +/-5-degree chamfers at the turning starting position and the turning finishing position;
2) cladding the alloy powder for laser repair of the large fan main shaft on the surface of the fan main shaft in a synchronous feeding mode;
3) stopping laser cladding after one layer of laser cladding is finished, brushing the slag on the cladding layer by using a polishing wheel until the slag is completely removed, and then cladding the next layer;
4) turning the fan main shaft subjected to cladding until the tolerance requirement is met, performing dye penetrant inspection, and if pore cracks are detected, removing a cladding layer by turning, and then returning to the step 2); and if pore-free cracks are detected, sending the turned fan main shaft into a heat treatment furnace for tempering, air-cooling to room temperature after tempering, performing dye-penetrant inspection again and performing hardness test, if pore-free cracks are detected and the hardness meets the requirement, completing laser repair, otherwise, removing a cladding layer by turning, and then returning to the step 2).
Further, during cladding in the step 2), the laser power is 5000 w-5900 w, the linear speed is 9.0-11 mm/s, the lap joint rate is 50-55%, and the cladding thickness is controlled to be 0.8-1.1 mm.
Further, in the step 4), the tempering temperature is 590-625 ℃, the temperature fluctuation is +/-10 ℃, and the tempering time is 5 +/-1 hour.
The alloy powder of the invention comprises the following components and contents:
1. the Cr and Ni components in the alloy powder are taken as main components and are close to the components in the base material (25Cr2Ni4MoV), so that the color, the thermal expansion coefficient and the comprehensive mechanical property of a cladding layer are close to the base material. In addition, the closer the main component of the cladding layer is to the main component of the base material, the better the fusion property of the cladding layer and the base material is, so that the better the comprehensive performance is caused, and the better the anti-cracking effect is.
2. C is also the main component, and the hardness of the cladding layer with the carbon content of 0.1 wt%, 0.15 wt%, 0.20 wt% and 0.25 wt% after tempering at 590-625 ℃ (± 10 ℃) is compared, so that the hardness of the cladding layer meets the requirement of 230-290 HB of the industrial standard and the enterprise standard requirement when the carbon content is in the range of 0.15 wt% to 0.20 wt%. Considering that the higher the carbon content, the greater the cracking tendency, the range of 0.15 to 0.18 wt% is selected.
3) Mn and Si are elements that steel (powder) must contain, and since the higher the Mn content is, the coarser the structure becomes, which is unfavorable for toughness, the lower the Si content is, the higher the hardness is, which is unfavorable for toughness, and the lower the silicon content is, the powder is reduced in oxygen removal and slag formation ability during cladding, and pores are easily generated, and it is found by experiments that: the comprehensive performance is the most excellent when the Si content is 0.3-0.6 wt%.
4) The content of B is an element for deoxidizing and slagging, is one of essential elements of self-fluxing alloy powder for laser cladding, is used together with Si, the higher the content of B is, the cladding layer has a great tendency to crack after cladding, the lower the content of B is, pores and slag inclusion are easy to generate, and when the content of B is in the range of 0.4-0.7 wt%, the color difference between the cladding layer and a base material and the hardness after tempering at 590-625 ℃ (± 10 ℃) both meet the standard.
5) The content of Nb and V is mainly refined grains, and the toughness and the strength are further improved. According to the principle of 'similar melting' in materials science. The content of V refers to the components of the base material, the aim is to better match with the base material and improve the comprehensive mechanical property, the content of Nb is added to strongly refine grains of high-temperature austenite through the precipitation of Nb at the temperature of above 850 ℃, the precipitation of Nb below 850 ℃ is nearly completed, V begins to precipitate further refined grains, the combination of Nb and V double-microalloy has substantial help to the whole cooling process, and in addition, because Nb is very active, Cr, Mo and Fe elements can easily react to form intermetallic compounds, so the industry has an unparalleled regulation: when the carbon content is in the range of 0.10-0.20 wt%, the Nb content of the alloy structural steel is lower than 0.1 wt%, and is selected to be 0.05-0.08 wt% through comprehensive test comparison.
6) The addition of Mo is to eliminate temper softening and temper brittleness, and excessively high Mo causes the generation of melt thickness cracks, so 0.2-0.5 wt% is selected.
Compared with the prior art, the invention has the following beneficial effects:
1. according to the alloy powder for laser repair of the large fan spindle and the laser repair method, the components of the coating are close to the base material without chromatic aberration, the thermal deformation is small, the structure is compact, the bonding force between the coating and the base material is firm, the fusion thickness is not cracked, so that the stripping risk of a cladding layer in service does not exist, the hardness after tempering meets the industrial standard, and the alloy powder is close to the components of the base material to be repaired and has good weldability. The method solves the problems of the existing repair method that the color difference between the cladding layer and the base material is inconsistent, the component difference between the base material and the cladding layer is too large, the cladding layer is peeled off, the fusion thickness is easy to crack, the tempering hardness is too high or too low, and the like, and is very suitable for repairing hundreds of thousands of fan main shafts with large movement.
2. The alloy powder for laser repair of the large fan spindle and the laser repair method provided by the invention have the cost which is only 2/3 of the cost of the existing alloy powder, and the production cost is greatly reduced.
Detailed Description
The present invention will be further described with reference to the following examples.
The following examples are given below for laser repair of a 2MPG5.8(6350) fan spindle.
Example 1
The alloy powder for laser repair of the main shaft of the large fan comprises the following components:
C：0.17wt％；
Cr：1.5wt％；
Ni：3.5wt％；
Mo：0.35wt％；
Mn：0.25wt％；
Nb：0.065wt％；
V：0.10wt％；
B：0.55wt％；
Si：0.45wt％；
the balance being Fe.
The powder of the components is prepared by a vacuumizing nitrogen atomization powder preparation method after being mixed in advance, and the particle size of the prepared powder is 75-120 microns.
A laser repairing method for a large fan spindle is based on the alloy powder for laser repairing of the large fan spindle and comprises the following steps:
1) removing a fatigue layer of the large fan main shaft by turning, and pouring 30-degree chamfers at the turning starting position and the turning finishing position;
2) cladding the alloy powder for laser repair of the large fan spindle on the surface of the fan spindle by adopting a synchronous feeding mode, wherein during cladding, the laser power is 5500w, the linear speed is 10mm/s, the lap joint rate is 55%, and the cladding thickness is controlled to be 1.0 mm;
3) stopping laser cladding after one layer of laser cladding is finished, brushing the slag on the cladding layer by using a polishing wheel until the slag is completely removed, and then cladding the next layer;
4) turning the fan main shaft subjected to cladding until the tolerance requirement is met, performing dye penetrant inspection, and if pore cracks are detected, removing a cladding layer by turning, and then returning to the step 2); and if pore-free cracks are detected, sending the turned fan main shaft into a heat treatment furnace for tempering, wherein the tempering temperature is 615 ℃, the temperature is +/-10 ℃ in a floating mode, the tempering time is 5 hours, air-cooling to room temperature after tempering, performing dye penetrant inspection and hardness testing again, if pore-free cracks are detected and the hardness meets the requirement, completing laser repair, otherwise, removing a cladding layer through turning, and returning to the step 2).
Example 2
The alloy powder for laser repair of the main shaft of the large fan comprises the following components:
C：0.16wt％；
Cr：1.3wt％；
Ni：3.1wt％；
Mo：0.25wt％；
Mn：0.2wt％；
Nb：0.05wt％；
V：0.08wt％；
B：0.45wt％；
Si：0.35wt％；
the balance being Fe.
The powder of the components is prepared by a vacuumizing nitrogen atomization powder preparation method after being mixed in advance, and the particle size of the prepared powder is 75-120 microns.
A laser repairing method for a large fan spindle is based on the alloy powder for laser repairing of the large fan spindle and comprises the following steps:
1) removing a fatigue layer of the large fan main shaft by turning, and pouring 30-degree chamfers at the turning starting position and the turning finishing position;
2) cladding the alloy powder for laser repair of the large fan spindle on the surface of the fan spindle by adopting a synchronous feeding mode, wherein during cladding, the laser power is 5300w, the linear speed is 11mm/s, the lap joint rate is 50%, and the cladding thickness is controlled to be 0.8 mm;
3) stopping laser cladding after one layer of laser cladding is finished, brushing the slag on the cladding layer by using a polishing wheel until the slag is completely removed, and then cladding the next layer;
4) turning the fan main shaft subjected to cladding until the tolerance requirement is met, performing dye penetrant inspection, and if pore cracks are detected, removing a cladding layer by turning, and then returning to the step 2); and if pore-free cracks are detected, sending the turned fan main shaft into a heat treatment furnace for tempering, wherein the tempering temperature is 625 ℃, the temperature is floated to +/-10 ℃, the tempering time is 5 hours, air cooling to room temperature after tempering, performing dye penetrant inspection and hardness test again, if pore-free cracks are detected and the hardness meets the requirement, completing laser repair, otherwise, removing a cladding layer through turning, and returning to the step 2).
Example 3
The alloy powder for laser repair of the main shaft of the large fan comprises the following components:
C：0.15wt％；
Cr：1.0wt％；
Ni：3.3wt％；
Mo：0.15wt％；
Mn：0.05wt％；
Nb：0.055wt％；
V：0.09wt％；
B：0.40wt％；
Si：0.55wt％；
the balance being Fe.
The powder of the components is prepared by a vacuumizing nitrogen atomization powder preparation method after being mixed in advance, and the particle size of the prepared powder is 75-120 microns.
A laser repairing method for a large fan spindle is based on the alloy powder for laser repairing of the large fan spindle and comprises the following steps:
1) removing a fatigue layer of the large fan main shaft by turning, and pouring 30-degree chamfers at the turning starting position and the turning finishing position;
2) cladding the alloy powder for laser repair of the large fan spindle on the surface of the fan spindle by adopting a synchronous feeding mode, wherein during cladding, the laser power is 5000w, the linear speed is 9mm/s, the lap joint rate is 52%, and the cladding thickness is controlled to be 0.9 mm;
3) stopping laser cladding after one layer of laser cladding is finished, brushing the slag on the cladding layer by using a polishing wheel until the slag is completely removed, and then cladding the next layer;
4) turning the fan main shaft subjected to cladding until the tolerance requirement is met, performing dye penetrant inspection, and if pore cracks are detected, removing a cladding layer by turning, and then returning to the step 2); and if pore-free cracks are detected, sending the turned fan main shaft into a heat treatment furnace for tempering, wherein the tempering temperature is 600 ℃, the temperature is +/-10 ℃ in a floating mode, the tempering time is 6 hours, air-cooling to room temperature after tempering, performing dye-based flaw detection and hardness testing again, completing laser repair if pore-free cracks are detected and the hardness meets the requirement, otherwise, removing a cladding layer through turning, and returning to the step 2).
Example 4
The alloy powder for laser repair of the main shaft of the large fan comprises the following components:
C：0.18wt％；
Cr：2.0wt％；
Ni：4.0wt％；
Mo：0.45wt％；
Mn：0.5wt％；
Nb：0.075wt％；
V：0.11wt％；
B：0.65wt％；
Si：0.6wt％；
the balance being Fe.
The powder of the components is prepared by a vacuumizing nitrogen atomization powder preparation method after being mixed in advance, and the particle size of the prepared powder is 75-120 microns.
A laser repairing method for a large fan spindle is based on the alloy powder for laser repairing of the large fan spindle and comprises the following steps:
1) removing a fatigue layer of the large fan main shaft by turning, and pouring 30-degree chamfers at the turning starting position and the turning finishing position;
2) cladding the alloy powder for laser repair of the large fan spindle on the surface of the fan spindle by adopting a synchronous feeding mode, wherein during cladding, the laser power is 5900w, the linear speed is 10mm/s, the lap joint rate is 54%, and the cladding thickness is controlled to be 1.1 mm;
3) stopping laser cladding after one layer of laser cladding is finished, brushing the slag on the cladding layer by using a polishing wheel until the slag is completely removed, and then cladding the next layer;
4) turning the fan main shaft subjected to cladding until the tolerance requirement is met, performing dye penetrant inspection, and if pore cracks are detected, removing a cladding layer by turning, and then returning to the step 2); and if pore-free cracks are detected, sending the turned fan main shaft into a heat treatment furnace for tempering, wherein the tempering temperature is 590 ℃, the temperature is floated to +/-10 ℃, the tempering time is 4 hours, air-cooling to room temperature after tempering, performing dye-based flaw detection again and performing hardness test, if pore-free cracks are detected and the hardness meets the requirement, completing laser repair, otherwise, removing a cladding layer through turning, and returning to the step 2).
Finally, it should be noted that: the above embodiments are only used for illustrating the technical solutions of the present invention, and not for limiting the same, and it is obvious for a person skilled in the art to modify the specific technical solutions described in the foregoing embodiments or to substitute part of the technical features, and these modifications or substitutions do not make the essence of the corresponding technical solutions depart from the scope of the technical solutions protected by the present invention.
Claims (9)
1. The alloy powder for laser repair of the main shaft of the large fan is characterized by comprising the following powder components:
C：0.15～0.18wt％；
Cr：1.0～2.0wt％；
Ni：3.0～4.0wt％；
Mo：0.2～0.5wt％；
Mn：0.0～0.5wt％；
Nb：0.05～0.08wt％；
V：0.08～0.12wt％；
B：0.4～0.7wt％；
Si：0.3～0.6wt％；
the balance being Fe.
2. The alloy powder for laser repair of the large fan main shaft according to claim 1, wherein:
the powder of each component is prepared by adopting a vacuumizing nitrogen atomization powder preparation method after being mixed in advance.
3. The alloy powder for laser repair of a large fan spindle according to claim 1 or 2, wherein:
the particle size of the prepared powder is 75-120 microns.
4. The alloy powder for laser repair of the large fan main shaft according to claim 3, wherein:
C：0.16～0.17wt％；
Cr：1.3～1.5wt％；
Ni：3.1～3.5wt％；
Mo：0.25～0.35wt％；
Mn：0.2～0.25wt％；
Nb：0.05～0.065wt％；
V：0.08～0.10wt％；
B：0.45～0.55wt％；
Si：0.35～0.45wt％；
the balance being Fe.
5. The alloy powder for laser repair of the large fan main shaft according to claim 4, wherein:
C：0.17wt％；
Cr：1.5wt％；
Ni：3.5wt％；
Mo：0.35wt％；
Mn：0.25wt％；
Nb：0.065wt％；
V：0.10wt％；
B：0.55wt％；
Si：0.45wt％；
the balance being Fe.
6. The alloy powder for laser repair of the large fan main shaft according to claim 4, wherein:
C：0.16wt％；
Cr：1.3wt％；
Ni：3.1wt％；
Mo：0.25wt％；
Mn：0.2wt％；
Nb：0.05wt％；
V：0.08wt％；
B：0.45wt％；
Si：0.35wt％；
the balance being Fe.
7. A laser repairing method for a large fan main shaft is characterized in that the alloy powder for laser repairing of the large fan main shaft based on any one of claims 1 to 6 comprises the following steps:
1) removing a fatigue layer of the large fan main shaft by turning, and pouring 30 +/-5-degree chamfers at the turning starting position and the turning finishing position;
2) cladding the alloy powder for laser repair of the large fan main shaft on the surface of the fan main shaft in a synchronous feeding mode;
3) stopping laser cladding after one layer of laser cladding is finished, brushing the slag on the cladding layer by using a polishing wheel until the slag is completely removed, and then cladding the next layer;
4) turning the fan main shaft subjected to cladding until the tolerance requirement is met, performing dye penetrant inspection, and if pore cracks are detected, removing a cladding layer by turning, and then returning to the step 2); and if pore-free cracks are detected, sending the turned fan main shaft into a heat treatment furnace for tempering, air-cooling to room temperature after tempering, performing dye-penetrant inspection again and performing hardness test, if pore-free cracks are detected and the hardness meets the requirement, completing laser repair, otherwise, removing a cladding layer by turning, and then returning to the step 2).
8. The laser repairing method for the main shaft of the large-scale wind turbine according to claim 7, characterized in that:
during cladding in the step 2), the laser power is 5000 w-5900 w, the linear speed is 9.0-11 mm/s, the lap joint rate is 50-55%, and the cladding thickness is controlled to be 0.8-1.1 mm.
9. The laser repairing method for the main shaft of the large-scale wind turbine according to claim 8, characterized in that:
in the step 4), the tempering temperature is 590-625 ℃, the temperature fluctuation is +/-10 ℃, and the tempering time is 5 +/-1 hour.
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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114622198A (en) * | 2021-11-25 | 2022-06-14 | 上海吴泾第二发电有限责任公司 | Power station generator rotor shaft neck damage laser cladding repair method and application |
| CN114892100A (en) * | 2022-05-09 | 2022-08-12 | 西安必盛激光科技有限公司 | Alloy powder for laser cladding of small cold-rolled working roll and cladding method |
| CN115369402A (en) * | 2022-08-26 | 2022-11-22 | 扬州镭奔激光科技有限公司 | Laser remanufacturing and forming process for ZM6 magnesium alloy part adopting self-fluxing alloy powder |
| CN115383118A (en) * | 2022-08-02 | 2022-11-25 | 浙江工业大学 | Preparation method of low alloy steel laser additive shaft repair part with excellent fatigue performance |
Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101381869A (en) * | 2008-10-22 | 2009-03-11 | 东莞理工学院 | Alloy powder special for laser-remelted high hardness crackless iron-base alloy |
| WO2018232618A1 (en) * | 2017-06-21 | 2018-12-27 | Höganäs Ab | Iron based alloy suitable for providing a hard and corrosion resistant coating on a substrate, article having a hard and corrosion resistant coating, and method for its manufacture |
| CN109536945A (en) * | 2018-11-30 | 2019-03-29 | 成都大陆激光技术有限公司 | A method of repairing generator rotor shaft neck |
| CN110157977A (en) * | 2019-04-25 | 2019-08-23 | 浙江工业大学 | A kind of laser remanufacturing reparation iron(-)base powder and the preparation method and application thereof |
| CN110484910A (en) * | 2019-08-19 | 2019-11-22 | 山东能源重装集团大族再制造有限公司 | A kind of laser cladding method of axis class and pipe type element |
| CN111945154A (en) * | 2020-08-06 | 2020-11-17 | 陕西陕北矿业有限责任公司 | Iron-based alloy powder for laser cladding and laser cladding method |
| CN112063934A (en) * | 2020-08-14 | 2020-12-11 | 浙江工业大学 | Laser cladding iron-based alloy powder for repairing steam turbine rotor shaft neck, and preparation and application thereof |
-
2020
- 2020-12-18 CN CN202011504724.1A patent/CN112725693A/en active Pending
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101381869A (en) * | 2008-10-22 | 2009-03-11 | 东莞理工学院 | Alloy powder special for laser-remelted high hardness crackless iron-base alloy |
| WO2018232618A1 (en) * | 2017-06-21 | 2018-12-27 | Höganäs Ab | Iron based alloy suitable for providing a hard and corrosion resistant coating on a substrate, article having a hard and corrosion resistant coating, and method for its manufacture |
| CN109536945A (en) * | 2018-11-30 | 2019-03-29 | 成都大陆激光技术有限公司 | A method of repairing generator rotor shaft neck |
| CN110157977A (en) * | 2019-04-25 | 2019-08-23 | 浙江工业大学 | A kind of laser remanufacturing reparation iron(-)base powder and the preparation method and application thereof |
| CN110484910A (en) * | 2019-08-19 | 2019-11-22 | 山东能源重装集团大族再制造有限公司 | A kind of laser cladding method of axis class and pipe type element |
| CN111945154A (en) * | 2020-08-06 | 2020-11-17 | 陕西陕北矿业有限责任公司 | Iron-based alloy powder for laser cladding and laser cladding method |
| CN112063934A (en) * | 2020-08-14 | 2020-12-11 | 浙江工业大学 | Laser cladding iron-based alloy powder for repairing steam turbine rotor shaft neck, and preparation and application thereof |
Non-Patent Citations (5)
| Title |
|---|
| 姜求志 等: "《火力发电厂金属材料手册》", 30 April 2001, 中国电力出版社 * |
| 澹台凡亮 等: "现场激光增材修复风机转子轴实验及组织性能研究", 《热喷涂技术》 * |
| 王琨 等: "《工程材料》", 29 February 2012, 华中科技大学出版社 * |
| 肖海兵 等: "《先进激光制造设备》", 30 March 2019, 华中科技大学出版社 * |
| 陈沪 等: "《激光熔覆与喷涂焊接实训教程》", 30 September 2017, 华南理工大学出版社 * |
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114622198A (en) * | 2021-11-25 | 2022-06-14 | 上海吴泾第二发电有限责任公司 | Power station generator rotor shaft neck damage laser cladding repair method and application |
| CN114892100A (en) * | 2022-05-09 | 2022-08-12 | 西安必盛激光科技有限公司 | Alloy powder for laser cladding of small cold-rolled working roll and cladding method |
| CN114892100B (en) * | 2022-05-09 | 2023-02-10 | 西安必盛激光科技有限公司 | Alloy powder for laser cladding of small cold-rolled working roll and cladding method |
| CN115383118A (en) * | 2022-08-02 | 2022-11-25 | 浙江工业大学 | Preparation method of low alloy steel laser additive shaft repair part with excellent fatigue performance |
| CN115369402A (en) * | 2022-08-26 | 2022-11-22 | 扬州镭奔激光科技有限公司 | Laser remanufacturing and forming process for ZM6 magnesium alloy part adopting self-fluxing alloy powder |
| CN115369402B (en) * | 2022-08-26 | 2023-12-01 | 扬州镭奔激光科技有限公司 | ZM6 magnesium alloy part laser remanufacturing technology adopting self-fluxing alloy powder |
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